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Skin of morphing wing and drive method thereof

A technology of variant wings and driving methods, applied in the directions of wings, aircraft parts, transportation and packaging, etc., can solve the problems that cannot meet the requirements of smooth surface, continuous and overall air tightness of the wing, internal structure of the wing, and driving methods. It can solve the problems of complex deformation control and low overall bearing capacity of the wing, so as to achieve the effect of light weight, large deformation and reliable performance.

Inactive Publication Date: 2010-05-19
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The role of the traditional skin is mainly to maintain the aerodynamic shape of the wing, bear and transmit the flight aerodynamic load, which obviously cannot meet the requirements of the variant wing.
[0003] At present, in the research of variant wing technology, the skin mainly adopts two forms: one is the skin made of flexible rubber material. Although this skin meets the requirements of wing deformation and air tightness, it is Improving the bearing capacity makes the internal structure, driving mode and deformation control of the wing very complicated, and the overall bearing capacity of the wing is not high; the other uses a piece-type movable traditional hard skin. Wing loading and variant requirements, but cannot meet the smooth, continuous and overall airtightness requirements of the wing surface, which compromises the aerodynamic efficiency of the variant wing

Method used

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  • Skin of morphing wing and drive method thereof
  • Skin of morphing wing and drive method thereof
  • Skin of morphing wing and drive method thereof

Examples

Experimental program
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Effect test

Embodiment 1

[0029] like figure 1 , figure 2 As shown, a variant wing skin is made of fiber-reinforced composite material 1, which is made of glass fiber, carbon fiber or aramid fiber prepreg, in two layers of fiber-reinforced A shape memory alloy actuator 2 is arranged between the composite materials 1, and the fiber reinforced composite material 1 and the shape memory alloy actuator 2 are pressed together into a corrugated configuration at 10°C; the troughs of the upper fiber reinforced composite material are filled with Silicon-based rubber 3; the shape memory alloy actuator 2 has a high-temperature memory linear shape; the shape memory alloy actuator 2 adopts a one-way shape memory alloy.

[0030] The driving method of the variant wing skin in this embodiment is:

[0031] The modified wing skin is installed on the driving guide rail, and a spring-type shape memory alloy driver is respectively installed on both sides of the modified wing skin through a reinforcement sheet, which is u...

Embodiment 2

[0036] like figure 1 , figure 2 As shown, a variant wing skin is made of fiber-reinforced composite material 1, and the fiber-reinforced composite material is made of fiber, made of glass fiber, carbon fiber or aramid fiber and resin matrix by conventional methods, A shape memory alloy actuator 2 is arranged between two layers of fiber-reinforced composite materials 1, and the fiber-reinforced composite material 1 and the shape memory alloy actuator 2 are pressed into a corrugated configuration at 40°C; the upper layer of fiber-reinforced Silicon-based rubber 3 is filled in the trough of the composite material; the shape memory alloy actuator 2 memorizes a linear shape at high temperature; the shape memory alloy actuator 2 adopts a two-way shape memory alloy, which memorizes a linear shape at high temperature and a corrugated shape at low temperature.

[0037] The driving method of the variant wing skin in this embodiment is:

[0038]Install the variant wing skin on the dri...

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Abstract

The invention provides a skin of a morphing wing, which is made from fiber-reinforced composite material (1). The skin is characterized in that: a shape memory alloy driver (2) is arranged between the two layers of the fiber-reinforced composite material (1); the wave trough of the upper layer fiber-reinforced composite material is internally filled with silica-based rubber (3) for meeting the requirements of smoothness, continuity and whole gas tightness on the surface of the wing; the fiber-reinforced composite material (1) and the shape memory alloy driver (2) are jointly pressed into to a corrugated structure under room temperature; the shape memory alloy driver (2) is in the shape of a high-temperature memory straight line; and the silica-based rubber (3) can be solidified under normal temperature. The invention also provides a drive method of the skin of the morphing wing. The skin of the morphing wing has the corrugated structure, thereby having high flexibility, large morphing amount and fast morphing response speed on the morphing direction, having high carrying capability on the perpendicular morphing direction, and having simple structure, light weight and reliable performance.

Description

technical field [0001] The invention relates to a variant wing skin, and also relates to a driving method of the variant wing skin. Background technique [0002] Variant aircraft is a hot topic in the current aircraft design field. It breaks the traditional aircraft design concept and can solve the technical problems existing in the current aircraft design. The wing has an extremely important influence on the lift-to-drag ratio, limit speed, maneuverability, control and stability, economy and safety of the aircraft. The traditional wing is fixed in design according to the requirements of the flight mission, and the aircraft relies on the hydraulic mechanical system to drive the aerodynamic rudder surface to realize flight control. Although this form of wing is easy to implement, the system is relatively complex and heavy, and its aerodynamic efficiency is not high. Therefore, the mission range of traditional aircraft and the ability to adapt to changes in atmospheric airfl...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/26
Inventor 王帮峰牟常伟陆孟雄芦吉云张立卞侃
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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